US5225016A - Method of manufacturing an advanced composite duct having integral ribs - Google Patents

Method of manufacturing an advanced composite duct having integral ribs Download PDF

Info

Publication number
US5225016A
US5225016A US07/739,403 US73940391A US5225016A US 5225016 A US5225016 A US 5225016A US 73940391 A US73940391 A US 73940391A US 5225016 A US5225016 A US 5225016A
Authority
US
United States
Prior art keywords
rings
ribs
spacers
bladder
preform
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
US07/739,403
Inventor
Branko Sarh
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rohr Inc
Original Assignee
Rohr Industries Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rohr Industries Inc filed Critical Rohr Industries Inc
Priority to US07/739,403 priority Critical patent/US5225016A/en
Assigned to ROHR INDUSTRIES, INC. reassignment ROHR INDUSTRIES, INC. ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: SARH, BRANKO
Assigned to ROHR, INC. A CORP. OF DE reassignment ROHR, INC. A CORP. OF DE CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). EFFECTIVE ON 12/13/1991 Assignors: ROHR INDUSTRIES, INC., A CORP. OF DE
Application granted granted Critical
Publication of US5225016A publication Critical patent/US5225016A/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Images

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29DPRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00Subject matter not provided for in other groups of this subclass
    • B29D99/001Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0014Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C53/00Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/22Corrugating
    • B29C53/30Corrugating of tubes
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/40Shaping or impregnating by compression not applied
    • B29C70/42Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/40Shaping or impregnating by compression not applied
    • B29C70/42Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B29C70/462Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29KINDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29LINDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2023/00Tubular articles
    • B29L2023/003Tubular articles having irregular or rough surfaces

Definitions

  • the invention relates in general to the manufacture of fiber reinforced resin composite ducts and, more particularly, to an improved method for manufacturing such ducts with integrally formed upstanding ribs.
  • Ducts of various shapes are widely used in aerospace and other applications. Often it is necessary that the ducts combine the lightest possible weight with high strength. This may be accomplished by forming the tubular duct and adding appropriately spaced external reinforcing ribs. With metal ducts, the ribs are generally applied by welding or riveting the ribs to the structure, methods that are time consuming, require considerable skill and generally add undesirable weight to the structure.
  • Simple ducts may be rapidly formed using filament winding processes where a resin impregnated fiber tow is wound around a mandrel, cured and removed. Adding reinforcing ribs to such structures has proved difficult. Generally, toroidal rib rings are formed by hand lay up, then bonded to the duct with adhesives or are co-cured with the duct, thereby requiring considerable hand work and complex tooling. Further, ducts made by these techniques often have a relative weak bond between duct and rib, requiring the use of additional material, with attendant undesirable weight increases, to assure adequate strength.
  • an object of this invention to provide a method of manufacturing advanced composite ribbed ducts having improved simplicity, uniformity and efficiency.
  • Another object is to provide a method of making ribbed ducts in which the ribs are integral with the duct for highest strength with lowest weight.
  • a further object is to provide a method of making ribbed ducts that have a high strength-to-weight ratio.
  • an inner advanced composite duct is made by filament winding and a second outer advanced composite duct having a generally cylindrical shape is formed by filament winding and reshaped to form integral ribs, then the inner duct, also having a generally cylindrical shape, is inserted into the outer duct and the assembly is co-cured under appropriate pressure and temperature to produce a high strength duct having a continuous smooth inner wall and integral exterior ribs.
  • the outer tube or duct is formed on a suitable generally cylindrically shaped mandrel having an inflatable surface bladder.
  • a basic tube is formed, for example, by filament winding a resin impregnated tow or tow band onto the mandrel surface.
  • the tube is filament wound in a helical pattern that permits localized deformation into radial rib shapes, as detailed below. Hoop winding of filaments should be avoided since such windings do not permit the required deformation.
  • a plurality of spaced rings are then clamped to the surface of the tube with spacers between adjacent rings, the spacers being out of contact with the tube along the outer edges of the rings.
  • the initial spacers are removed and replaced with narrower spacers which are out of contact with the ribs.
  • the rings are moved toward each other into contact with the narrow second spacers, resulting in shallow ribs forming by distortion of the helically wound tube between the rings. This procedure is repeated with progressively narrower spacers to carefully form progressively higher and thinner ribs.
  • the spacers may be removed and the rings pressed together, to form thin ribs from the tube material.
  • an inner tube of slightly less diameter is formed by, for example, filament winding on a mandrel having an inflatable surface bladder.
  • the mandrel is removed from the outer tube, then the assembly of inner tube and mandrel is inserted therein.
  • the resin is a preferred thermosetting resin, the assembly is vacuum bagged, the bladder on the inner mandrel is inflated and the resin is co-cured in an autoclave to produce an integrally ribbed duct having a smooth, uniform internal surface.
  • the outer tube may be used alone in some applications. If a thermoplastic matrix resin is used, the resin will be kept above its softening temperature during the forming steps and co-consolidation of the two ducts and will be cooled to harden.
  • FIG. 1 is a schematic perspective of a filament wound tubular structure
  • FIG. 2 is a schematic perspective of the tube of FIG. 1 with clamp rings and spacers in place;
  • FIG. 3 is an axial section view through the assembly of FIG. 2, taken on line 3--3 in FIG. 2;
  • FIG. 3a is a detail section view of a portion of FIG. 3 showing the spacers replaced with narrower spacers;
  • FIG. 4 is a detail section view as in taken as in FIG. 3 illustrating the initial rib forming step
  • FIG. 5 is a detail section view taken as in FIG. 3 illustrating the final rib forming step
  • FIG. 6 is a section view taken as in FIG. 3 illustrating the insertion of the inner tube.
  • FIG. 7 is a perspective of the final integrally ribbed duct.
  • the first step is to deposit resin impregnated fibers, such as by filament winding in a helical pattern to form the basic outer tube 10 on a mandrel mounted for rotation on shaft 12.
  • mandrel 14 includes an inner hollow core 16 that may be any suitable material, such as aluminum, having positioned over its surface an inflatable reusable elastic bladder 18.
  • a plurality of small holes 17 may be provided through the wall of inner core 16 to provide internal pressurization of bladder 18.
  • bladder 18 may also be the internally pressurized type, obviating the need for holes 17.
  • Tube 10 may be formed from any suitable high strength fibers, such as graphite, Kevlar aramid, or mixed fibers, in any suitable matrix resin such as suitable thermosetting resins in the "B-stage" degree of cure or suitable thermoplastic resins.
  • the filament winding is conducted in a conventional manner, typically forming a helical fiber pattern without any hoop windings.
  • Rings 20 are preferably segmented to provide easy application and removal and are preferably clamped in place by conventional clamps, such as band clamps (not shown) around each ring. Rings 20 are uniformly spaced apart by spacers 22, which extend only partially into the space between adjacent rings 20 and are well out of contact with tube 10. The thicknesses of the various spacers 22 or rings 20 may be uniform or non-uniform to provide the pattern of ribs and rib heights desired for a particular application.
  • the first step in forming outwardly extending circumferential ribs integral with tube 10 is shown in a detail section view in FIG. 4.
  • the original spacers 22 shown in FIG. 3 are removed and narrower spacers 22a are inserted in their place after the initial set-up has confirmed the correct placement of rings 20 and spacers 22a. Spacers will not fill the spaces between rings 20 and will be suspended within the space by any conventional means, such as sleeves, the ring clamps or other means (not shown) engaging the outer surface of rings 20.
  • the rings 20, which are tightly clamped against the filament wound outer composite tube 10 are moved toward the center of the tube length as indicated by arrows 24 by any suitable conventional clamp or drive means (not shown) while bladder 18 is inflated to exert outward pressure on tube 10 as indicated by arrows 26.
  • bladder 18 is inflated to exert outward pressure on tube 10 as indicated by arrows 26.
  • This causes the tube 10, which is in an uncured, pliable, deformable state, to stretch radially outwardly into the space between rings 20 to form initial ribs 28.
  • the width of the initial spacers 20 bears a direct relationship to the height of rib 28 to be formed. Where a thin, maximum height rib is formed, the final rib 28 will have a height approximately half the space between the adjacent rings 20. If the rib 28 is hollow or shallow, the rib will have a height less than one-half the spacing of those rings 20. Also, rings 20 are all simultaneously moved or translated toward the longitudinal center of the tubular preform 10 as bladder 16 deforms preform 10 radially to compensate for the amount of preform material that is being used to form radial ribs 28.
  • Bladder 18 may be inflated during the first few steps of moving rings 20 against narrower spacers 22a, but as the ribs become narrower bladder 18 is no longer inflated, since it could be trapped within the thinner ribs. I have found that performing the rib forming in several steps results in ribs of more uniform quality, possibly because the stepwise forming allows time for any necessary slipping of fibers in the often viscous matrix resin. The number of steps required to produce an optimum structure with a particular combination of resin and fiber in tube 10 can easily be determined empirically with a short series of tests.
  • An inner tube or duct 30 is then formed in the same manner as shown in FIG. 1.
  • the same sort of mandrel having an inflatable surface bladder is used, with the diameters of the assembled mandrel, bladder and inner tube 30 being selected so that the outer diameter of the inner tube is substantially equal to or slightly less than the inner diameter of the outer tube. So as to permit inner tube 30 to be easily slid into the deformed outer duct 10.
  • Inner tube 30 is formed on a mandrel 14 having a core 16, with holes 17 and a suitable reusable inflatable bladder 18 of the sort used to make outer tube 10. While any suitable combination of fiber and resin may be used in inner tube 30, generally, they are the same as used for outer tube 10.
  • Inner tube 30 has an outside diameter substantially equal to the inner diameter of outer tube 10, or slightly less to provide easy insertion.
  • outer tube 10 The closed ends of outer tube 10 are cut off and the inner tube 30 is inserted therein, as indicated by arrow 32.
  • bladder 18 When fully inserted, bladder 18 is inflated and, if thermosetting resins are used, the assembly is heated to the curing temperature of the resin. While cure may be accomplished in any suitable manner, generally it is done by vacuum bagging the assembly and heating it to the curing temperature for an appropriate time while being subjected to a predetermined pressure.
  • thermoplastic resins are used for the manufacture of the duct, the assembly as shown in FIG. 6 is held at the softening temperature of the resin, bladder 18 if inflated to press inner tube 30 against ribbed outer tube 10 for co-consolidation of tubes 10 and 30 and the assembly is allowed to cool to solidify the tubes which are bonded to form a single unitary duct.
  • Duct 40 has a multi-layer tube 42 and a plurality of highly uniform ribs 44 that are integral with the outer layers of tube 42 so that the attachment lines between ribs and tube are of the highest possible strength.
  • duct 40 is shown as a unitary duct having integral ribs resulting from the unique process of this invention and an inner tube bonded to the formed outer duct, if desired the inner duct could be omitted.
  • the method of filament winding tubes 10 and 30 described above are preferred, if desired, those tubes could be formed from other materials by other methods, so long as the material of outer tube 10 is capable of the required deformation in the method of this invention.
  • one or both of tubes 10 and 30 could be formed by processes such as tape laying, injection molding, resin transfer molding and the like.
  • the basic tubes 10 and 30 could be made by conventional hand lay-up of fiber containing pre-preg materials. Any suitable means may be used for moving rings 20 toward each other, such as a lead screw mechanism. While the above description of preferred embodiments illustrate formation of rings on the exterior of the duct, ribs could be formed on the interior of a duct by this method.

Abstract

A method of making ducts having outwardly extending ribs formed integrally with the duct structure. Two tubes are formed from fiber reinforced resin materials, a uniform inner tube and a ribbed outer tube, then the inner tube is bonded with in the outer tube to form a high strength ribbed duct. An outer tube is formed by placing resin impregnated fibers over a cylindrical mandrel having an inflatable bladder on its surface, placing a plurality of spaced rings tightly against the outer surface, pressurizing the bladder to expand the tube into the spaces between rings to form low ribs, then gradually moving the rings toward each other to press the ribs therebetween and form thin upstanding ribs. The inner tube is formed by placing resin impregnated fibers on a slightly thinner mandrel that also has a surface bladder. When both tubes are formed, the mandrel is removed from the outer tube and the inner tube and mandrel are inserted therein and the inner tube bladder is inflated. The assembly is vacuum bagged and cured in an autoclave at a suitable temperature. The rings and mandrel are then removed and an integrally ribbed duct results. The thermosetting or thermoplastic resin impregnated fiber material may be placed on the mandrels by any suitable means such as filament winding, hand lay-up, or other deposition techniques.

Description

BACKGROUND OF THE INVENTION
The invention relates in general to the manufacture of fiber reinforced resin composite ducts and, more particularly, to an improved method for manufacturing such ducts with integrally formed upstanding ribs.
Ducts of various shapes are widely used in aerospace and other applications. Often it is necessary that the ducts combine the lightest possible weight with high strength. This may be accomplished by forming the tubular duct and adding appropriately spaced external reinforcing ribs. With metal ducts, the ribs are generally applied by welding or riveting the ribs to the structure, methods that are time consuming, require considerable skill and generally add undesirable weight to the structure.
Recently, ducts formed from high strength fibers imbedded in a plastic resin matrix have come into use due to their high strength to weight ratio. Typical of filament winding processes are those described by Bluck in U.S. Pat. No. 3,210,228 and Carter in U.S. Pat. No. 3,303,079.
Simple ducts may be rapidly formed using filament winding processes where a resin impregnated fiber tow is wound around a mandrel, cured and removed. Adding reinforcing ribs to such structures has proved difficult. Generally, toroidal rib rings are formed by hand lay up, then bonded to the duct with adhesives or are co-cured with the duct, thereby requiring considerable hand work and complex tooling. Further, ducts made by these techniques often have a relative weak bond between duct and rib, requiring the use of additional material, with attendant undesirable weight increases, to assure adequate strength.
Thus, there is a continuing need for an improved method of manufacturing ribbed composite ducts having increased strength and lighter weight while permitting more rapid and efficient manufacture.
SUMMARY OF THE INVENTION
It is, therefore, an object of this invention to provide a method of manufacturing advanced composite ribbed ducts having improved simplicity, uniformity and efficiency.
Another object is to provide a method of making ribbed ducts in which the ribs are integral with the duct for highest strength with lowest weight.
A further object is to provide a method of making ribbed ducts that have a high strength-to-weight ratio.
The above-noted objects, and others, are accomplished in accordance with this invention by a method in which, in a preferred embodiment, an inner advanced composite duct is made by filament winding and a second outer advanced composite duct having a generally cylindrical shape is formed by filament winding and reshaped to form integral ribs, then the inner duct, also having a generally cylindrical shape, is inserted into the outer duct and the assembly is co-cured under appropriate pressure and temperature to produce a high strength duct having a continuous smooth inner wall and integral exterior ribs.
The outer tube or duct is formed on a suitable generally cylindrically shaped mandrel having an inflatable surface bladder. A basic tube is formed, for example, by filament winding a resin impregnated tow or tow band onto the mandrel surface. The tube is filament wound in a helical pattern that permits localized deformation into radial rib shapes, as detailed below. Hoop winding of filaments should be avoided since such windings do not permit the required deformation.
A plurality of spaced rings are then clamped to the surface of the tube with spacers between adjacent rings, the spacers being out of contact with the tube along the outer edges of the rings. After this initial set up to accurately position the rings, the initial spacers are removed and replaced with narrower spacers which are out of contact with the ribs. As the internal bladder is pressurized, the rings are moved toward each other into contact with the narrow second spacers, resulting in shallow ribs forming by distortion of the helically wound tube between the rings. This procedure is repeated with progressively narrower spacers to carefully form progressively higher and thinner ribs. Finally, the spacers may be removed and the rings pressed together, to form thin ribs from the tube material.
As the material from the outer tube is thus distorted into the spaces between the rings it will be understood that the overall length of the tube will be lessened to accommodate the material being utilized to form the ribs.
Meanwhile, an inner tube of slightly less diameter is formed by, for example, filament winding on a mandrel having an inflatable surface bladder. When both tubes are complete, the mandrel is removed from the outer tube, then the assembly of inner tube and mandrel is inserted therein. If the resin is a preferred thermosetting resin, the assembly is vacuum bagged, the bladder on the inner mandrel is inflated and the resin is co-cured in an autoclave to produce an integrally ribbed duct having a smooth, uniform internal surface.
While the use of an inner tube within the integrally ribbed water tube is preferred for optimum strength, if desired the outer tube may be used alone in some applications. If a thermoplastic matrix resin is used, the resin will be kept above its softening temperature during the forming steps and co-consolidation of the two ducts and will be cooled to harden.
BRIEF DESCRIPTION OF THE DRAWINGS
Details of the invention, and of preferred embodiments thereof, will be further understood upon reference to the drawing, wherein:
FIG. 1 is a schematic perspective of a filament wound tubular structure;
FIG. 2 is a schematic perspective of the tube of FIG. 1 with clamp rings and spacers in place;
FIG. 3 is an axial section view through the assembly of FIG. 2, taken on line 3--3 in FIG. 2;
FIG. 3a is a detail section view of a portion of FIG. 3 showing the spacers replaced with narrower spacers;
FIG. 4 is a detail section view as in taken as in FIG. 3 illustrating the initial rib forming step;
FIG. 5 is a detail section view taken as in FIG. 3 illustrating the final rib forming step;
FIG. 6 is a section view taken as in FIG. 3 illustrating the insertion of the inner tube; and
FIG. 7 is a perspective of the final integrally ribbed duct.
DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS
As seen in FIG. 1 the first step is to deposit resin impregnated fibers, such as by filament winding in a helical pattern to form the basic outer tube 10 on a mandrel mounted for rotation on shaft 12. As best seen in FIG. 3, mandrel 14 includes an inner hollow core 16 that may be any suitable material, such as aluminum, having positioned over its surface an inflatable reusable elastic bladder 18. A plurality of small holes 17 may be provided through the wall of inner core 16 to provide internal pressurization of bladder 18. Alternatively, bladder 18 may also be the internally pressurized type, obviating the need for holes 17.
Tube 10 may be formed from any suitable high strength fibers, such as graphite, Kevlar aramid, or mixed fibers, in any suitable matrix resin such as suitable thermosetting resins in the "B-stage" degree of cure or suitable thermoplastic resins. The filament winding is conducted in a conventional manner, typically forming a helical fiber pattern without any hoop windings.
Next, as shown in FIGS. 2 and 3, a plurality of spaced rings 20 is placed over outer tube 10. Rings 20 are preferably segmented to provide easy application and removal and are preferably clamped in place by conventional clamps, such as band clamps (not shown) around each ring. Rings 20 are uniformly spaced apart by spacers 22, which extend only partially into the space between adjacent rings 20 and are well out of contact with tube 10. The thicknesses of the various spacers 22 or rings 20 may be uniform or non-uniform to provide the pattern of ribs and rib heights desired for a particular application.
The first step in forming outwardly extending circumferential ribs integral with tube 10 is shown in a detail section view in FIG. 4. The original spacers 22 shown in FIG. 3 are removed and narrower spacers 22a are inserted in their place after the initial set-up has confirmed the correct placement of rings 20 and spacers 22a. Spacers will not fill the spaces between rings 20 and will be suspended within the space by any conventional means, such as sleeves, the ring clamps or other means (not shown) engaging the outer surface of rings 20. Then the rings 20, which are tightly clamped against the filament wound outer composite tube 10, are moved toward the center of the tube length as indicated by arrows 24 by any suitable conventional clamp or drive means (not shown) while bladder 18 is inflated to exert outward pressure on tube 10 as indicated by arrows 26. This causes the tube 10, which is in an uncured, pliable, deformable state, to stretch radially outwardly into the space between rings 20 to form initial ribs 28.
The width of the initial spacers 20 bears a direct relationship to the height of rib 28 to be formed. Where a thin, maximum height rib is formed, the final rib 28 will have a height approximately half the space between the adjacent rings 20. If the rib 28 is hollow or shallow, the rib will have a height less than one-half the spacing of those rings 20. Also, rings 20 are all simultaneously moved or translated toward the longitudinal center of the tubular preform 10 as bladder 16 deforms preform 10 radially to compensate for the amount of preform material that is being used to form radial ribs 28.
If only shallow, open ribs are desired, one could go immediately to the operation shown in FIG. 6. However, generally thin ribs of substantially uniform thickness are desired. In that case, spacers 22a are removed and still narrower spacers are inserted and the movement of rings 20 is repeated to increase the height and narrow the base of ribs 28.
Bladder 18 may be inflated during the first few steps of moving rings 20 against narrower spacers 22a, but as the ribs become narrower bladder 18 is no longer inflated, since it could be trapped within the thinner ribs. I have found that performing the rib forming in several steps results in ribs of more uniform quality, possibly because the stepwise forming allows time for any necessary slipping of fibers in the often viscous matrix resin. The number of steps required to produce an optimum structure with a particular combination of resin and fiber in tube 10 can easily be determined empirically with a short series of tests.
Once the ribs 28 are fairly narrow, the spacers 22 are entirely removed, the bladder 18 is not inflated so that bladder material does not extend up into the narrow ribs 28 and rings 20 are brought tightly together as shown in FIG. 5. This final step produces ribs of even thickness, or any other desired configuration as determined by the shape and angle of the faces of rings 20 that press against ribs 28.
An inner tube or duct 30 is then formed in the same manner as shown in FIG. 1. The same sort of mandrel having an inflatable surface bladder is used, with the diameters of the assembled mandrel, bladder and inner tube 30 being selected so that the outer diameter of the inner tube is substantially equal to or slightly less than the inner diameter of the outer tube. So as to permit inner tube 30 to be easily slid into the deformed outer duct 10.
The final step is the insertion of inner tube 30 into outer tube 10. Inner tube 30 is formed on a mandrel 14 having a core 16, with holes 17 and a suitable reusable inflatable bladder 18 of the sort used to make outer tube 10. While any suitable combination of fiber and resin may be used in inner tube 30, generally, they are the same as used for outer tube 10. Inner tube 30 has an outside diameter substantially equal to the inner diameter of outer tube 10, or slightly less to provide easy insertion.
The closed ends of outer tube 10 are cut off and the inner tube 30 is inserted therein, as indicated by arrow 32. When fully inserted, bladder 18 is inflated and, if thermosetting resins are used, the assembly is heated to the curing temperature of the resin. While cure may be accomplished in any suitable manner, generally it is done by vacuum bagging the assembly and heating it to the curing temperature for an appropriate time while being subjected to a predetermined pressure.
If thermoplastic resins are used for the manufacture of the duct, the assembly as shown in FIG. 6 is held at the softening temperature of the resin, bladder 18 if inflated to press inner tube 30 against ribbed outer tube 10 for co-consolidation of tubes 10 and 30 and the assembly is allowed to cool to solidify the tubes which are bonded to form a single unitary duct.
The ends of inner tube 30 are cut off, mandrel 14 is removed, the rings 14 are removed, any flash such as might have formed between ring segments is trimmed and the integrally ribbed duct 40 as shown in FIG. 7 is complete. Duct 40 has a multi-layer tube 42 and a plurality of highly uniform ribs 44 that are integral with the outer layers of tube 42 so that the attachment lines between ribs and tube are of the highest possible strength.
While duct 40 is shown as a unitary duct having integral ribs resulting from the unique process of this invention and an inner tube bonded to the formed outer duct, if desired the inner duct could be omitted. While the method of filament winding tubes 10 and 30 described above are preferred, if desired, those tubes could be formed from other materials by other methods, so long as the material of outer tube 10 is capable of the required deformation in the method of this invention. For example, one or both of tubes 10 and 30 could be formed by processes such as tape laying, injection molding, resin transfer molding and the like. If desired, the basic tubes 10 and 30 could be made by conventional hand lay-up of fiber containing pre-preg materials. Any suitable means may be used for moving rings 20 toward each other, such as a lead screw mechanism. While the above description of preferred embodiments illustrate formation of rings on the exterior of the duct, ribs could be formed on the interior of a duct by this method.
Other applications, variations and ramifications of this invention will occur to those skilled in the art upon reading this disclosure. Those are intended to be included within the scope of this invention, as defined in the appended claims.

Claims (11)

I claim:
1. A method of manufacturing a tube with integral ribs which comprise the steps of:
preparing a tube preform by placing resin impregnated fibers in a selected pattern over a cylindrical mandrel having an inflatable bladder disposed on its surface;
placing a plurality of spaced rings against said tube preform;
placing a plurality of spacers of selected thickness between said rings to provide space between said rings;
clamping said spaced rings tightly against the surface of said tube preform;
inflating said bladder to cause said tube preform to expand into the space between said rings to form shallow ribs;
deflating said bladder and removing said spacers;
moving said rings together into pressure contact with said ribs;
removing said mandrel;
hardening said resin; and
removing said rings to form a unitary tube with integral ribs.
2. The method according to claim 1 further including, after the formation of said shallow ribs, at least once removing said spacers, replacing them with thinner spacers and moving said rings towards each other into contact with said spacers to increase height and decrease width of said ribs.
3. The method according to claim 1 wherein said resin is a thermosetting resin and said resin is hardened by vacuum bagging and heating said assembly to a suitable curing temperature in an autoclave.
4. The method according to claim 1 wherein said resin is a thermoplastic resin having a resin softening and solidification temperature and including the step of heating said impregnated fibers to the resin softening temperature prior to the forming steps and maintaining the preform at that temperature for consolidation, the reducing the temperature to the solidification temperature of the resins.
5. A method of manufacturing ducts with integral ribs which comprises the steps of:
preparing an inner tube preform by placing resin impregnated fiber in a selected pattern over a surface of a first cylindrical mandrel having a first inflatable surface bladder;
preparing an outer tube preform by placing resin impregnated fiber in a selected patter over a surface of a second cylindrical mandrel having a second inflatable surface bladder;
the inside diameter of said outer tube preform being less than the outside diameter of said inner tube preform;
placing a plurality of spaced rings against said outer preform;
placing a plurality of spacers of selected thickness between said rings to provide space between said rings;
clamping said spaced rings tightly against the surface of said outer preform;
inflating said second bladder to cause said second tube preform to expand into the space between said rings to form shallow ribs;
moving said rings together into pressure contact with said ribs;
removing said second mandrel;
inserting said first mandrel and inner tube preform into said second tube preform;
inflating said first bladder to press said inner tube preform tightly against said outer tube preform;
curing said rings in said preform; and
removing said rings to from a unitary duct with integral ribs.
6. The method according to claim 5 further including, after the formation of said shallow ribs, at least once removing said spacers, replacing them with thinner spacers and moving said rings towards each other into contact with said spacers to increase height and decrease width of said ribs.
7. The method according to claim 5 wherein said rings are thermosetting resins and said reins are cured by vacuum bagging and heating said assembly to suitable temperatures in an autoclave.
8. The method according to claim 5 wherein said resins are thermoplastic resins having a resin softening and solidification temperature and including the step of heating said impregnated fibers to the resin softening temperature prior to the forming steps and maintaining the preforms at that temperature until consolidation, then reducing the temperature to the solidification temperature of the resins.
9. The method of manufacturing ducts having integral ribs which comprise the steps of:
preparing an inner tube preform by placing resin impregnated fibers in a selected pattern over a surface of a first cylindrical mandrel having a first inflatable surface bladder;
preparing an outer tube preform by placing resin impregnated fibers in a selected pattern over a surface of a second cylindrical mandrel having a second inflatable surface bladder;
the inside diameter of said outer tube preform being no less than, the outside diameter of sid inner tube preform;
placing a plurality of spaced rings against said outer tube preform;
placing a plurality of spacers of selected thickness between said rings to provide space between said rings;
clamping said spaced rings tightly against the surface of said outer tube preform;
inflating said second bladder to cause said second tube preform to expand into the space between said rings to form shallow ribs;
at least once replacing said spacers with narrower spacers and moving rings together into contact with the narrower spacers to form ribs with increasing heights and widths;
after the selected number of steps of replacing spacers and moving rings together, removing the spacers entirely and moving said rings together into contact with said ribs;
removing said second mandrel;
inserting the first mandrel and inner tube preform into said second tube preform;
inflating said first bladder to press said inner tube preform tightly against said outer tube preform;
curing said resins in said preform and
removing said rings to form a unitary duct with integral ribs.
10. The method according to claim 9 wherein said resins are thermosetting resins and said resins are cured by vacuum bagging and heating said assembly to a suitable temperature in an autoclave.
11. The method according to claim 9 wherein said resins are thermoplastic resins and including the step of heating said impregnated fibers to the resin softening temperature prior to the forming steps and maintaining the preforms at that temperature until consolidation, then reducing the temperature to the solidification temperature of the resins.
US07/739,403 1991-08-02 1991-08-02 Method of manufacturing an advanced composite duct having integral ribs Expired - Fee Related US5225016A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US07/739,403 US5225016A (en) 1991-08-02 1991-08-02 Method of manufacturing an advanced composite duct having integral ribs

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/739,403 US5225016A (en) 1991-08-02 1991-08-02 Method of manufacturing an advanced composite duct having integral ribs

Publications (1)

Publication Number Publication Date
US5225016A true US5225016A (en) 1993-07-06

Family

ID=24972132

Family Applications (1)

Application Number Title Priority Date Filing Date
US07/739,403 Expired - Fee Related US5225016A (en) 1991-08-02 1991-08-02 Method of manufacturing an advanced composite duct having integral ribs

Country Status (1)

Country Link
US (1) US5225016A (en)

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5685933A (en) * 1993-04-26 1997-11-11 Toyota Jidosha Kabushiki Kaisha Method of manufacturing a drive shaft
US6110407A (en) * 1997-05-02 2000-08-29 Callaway Golf Company Methods of manufacturing dipped bladder molding mandrels for manufacturing tubular shafts
US6364649B1 (en) 1999-10-07 2002-04-02 Fibrex Insulations, Inc. Apparatus for making pipe insulation
US6586110B1 (en) 2000-07-07 2003-07-01 Delphi Technologies, Inc. Contoured metal structural members and methods for making the same
EP1342556A1 (en) * 2002-03-09 2003-09-10 Airbus Deutschland GmbH Process for producing a fiber reinforced composite component
US20040026015A1 (en) * 2002-08-09 2004-02-12 The Boeing Company Consolidation joining of thermoplastic laminate ducts
US20040026825A1 (en) * 2002-08-09 2004-02-12 The Boeing Company Preforming thermoplastic ducts
US20040026819A1 (en) * 2002-08-09 2004-02-12 The Boeing Company Post-forming of thermoplastic ducts
US20040028365A1 (en) * 2002-08-09 2004-02-12 Abds-Sami Malik Metal oxide coated fiber and methods for coating an optical fiber with a metal oxide coating
US6821638B2 (en) 2000-07-07 2004-11-23 Delphi Technologies, Inc. Shaped contoured crushable structural members and methods for making the same
US6949282B2 (en) 2000-07-07 2005-09-27 Delphi Technologies, Inc. Contoured crushable composite structural members and methods for making the same
US7097804B2 (en) 2002-08-09 2006-08-29 The Boeing Company Thermoplastic laminate duct
US7182293B2 (en) 2004-04-27 2007-02-27 The Boeing Company Airfoil box and associated method
US20080016844A1 (en) * 2006-07-19 2008-01-24 Shutrump Jeffrey D Aircraft engine inlet having zone of deformation
EP2045069A1 (en) * 2007-10-04 2009-04-08 The Goodyear Tire & Rubber Company Tire bead separation method and device
US20090308477A1 (en) * 2008-06-13 2009-12-17 Geislinger Gmbh Method for manufacturing a hollow shaft with at least one integral flange made of fiber composite
CN106493965A (en) * 2016-10-21 2017-03-15 北京化工大学 A kind of continuously elongated device and method for strengthening composite plastic pipe
US10006568B2 (en) 2016-06-06 2018-06-26 United Technologies Corporation Double walled tube and manufacture thereof
EP3342584A1 (en) * 2016-12-30 2018-07-04 Airbus Operations GmbH Membrane tool for reshaping reinforcing fibre layers for pre-shaped t-shaped profiles
US11260605B2 (en) 2020-01-21 2022-03-01 Goodrich Corporation Flexible thermoplastic composite coupling and method of manufacture
US11273610B2 (en) * 2019-03-21 2022-03-15 Goodrich Corporation Manufacturing methods for composite driveshafts

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3033730A (en) * 1956-11-07 1962-05-08 Smith Corp A O Method of forming a prestressed article of fiber reinforced resin
US3210228A (en) * 1961-07-06 1965-10-05 Trw Inc Method and apparatus for making a filament wound pressure vessel
US3303079A (en) * 1963-08-23 1967-02-07 Richard P Carter Method of manufacture of rocket chambers having an integral insulator or liner
US3833699A (en) * 1971-10-26 1974-09-03 Norbalt Rubber Corp Method of forming corrugated tubing using a mandrel having inflatable sleeves adjacent the ends
US3962394A (en) * 1975-06-02 1976-06-08 Trw Inc. Method for molding fiber reinforced composite tube
US4113828A (en) * 1976-04-12 1978-09-12 Kramer Sr Vance M Method for making flexible corrugated rubber tubing and tubing produced thereby
US4335587A (en) * 1979-07-11 1982-06-22 Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung Universal coupling member for two shafts and method of manufacturing such a coupling member
WO1987003534A1 (en) * 1985-12-12 1987-06-18 Keith Stewart Reinforced articles and method of their manufacture by means of inflatable moulds
US4891083A (en) * 1986-03-28 1990-01-02 Societe Anonyme:Societe Europeenne De Propulsion Method for producing a laminated composite structure including tubular braided reinforcement
US4986863A (en) * 1987-09-28 1991-01-22 Societe Europeenne De Propulsion Process for producing a laminated tubular fibrous structure for use as reinforcing structure for a composite piece
US5106442A (en) * 1989-07-07 1992-04-21 Uranit Gmbh Method for producing collar reinforcements on cylindrical composite fiber bodies
US5135596A (en) * 1990-02-23 1992-08-04 Deutsche Forschungsanstalt Fur Luft- Und Raumfahrt E.V. Process for manufacturing flanged tubular members from fiber composites

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3033730A (en) * 1956-11-07 1962-05-08 Smith Corp A O Method of forming a prestressed article of fiber reinforced resin
US3210228A (en) * 1961-07-06 1965-10-05 Trw Inc Method and apparatus for making a filament wound pressure vessel
US3303079A (en) * 1963-08-23 1967-02-07 Richard P Carter Method of manufacture of rocket chambers having an integral insulator or liner
US3833699A (en) * 1971-10-26 1974-09-03 Norbalt Rubber Corp Method of forming corrugated tubing using a mandrel having inflatable sleeves adjacent the ends
US3962394A (en) * 1975-06-02 1976-06-08 Trw Inc. Method for molding fiber reinforced composite tube
US4113828A (en) * 1976-04-12 1978-09-12 Kramer Sr Vance M Method for making flexible corrugated rubber tubing and tubing produced thereby
US4335587A (en) * 1979-07-11 1982-06-22 Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschraenkter Haftung Universal coupling member for two shafts and method of manufacturing such a coupling member
WO1987003534A1 (en) * 1985-12-12 1987-06-18 Keith Stewart Reinforced articles and method of their manufacture by means of inflatable moulds
US4891083A (en) * 1986-03-28 1990-01-02 Societe Anonyme:Societe Europeenne De Propulsion Method for producing a laminated composite structure including tubular braided reinforcement
US4986863A (en) * 1987-09-28 1991-01-22 Societe Europeenne De Propulsion Process for producing a laminated tubular fibrous structure for use as reinforcing structure for a composite piece
US5106442A (en) * 1989-07-07 1992-04-21 Uranit Gmbh Method for producing collar reinforcements on cylindrical composite fiber bodies
US5135596A (en) * 1990-02-23 1992-08-04 Deutsche Forschungsanstalt Fur Luft- Und Raumfahrt E.V. Process for manufacturing flanged tubular members from fiber composites

Cited By (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5685933A (en) * 1993-04-26 1997-11-11 Toyota Jidosha Kabushiki Kaisha Method of manufacturing a drive shaft
US6110407A (en) * 1997-05-02 2000-08-29 Callaway Golf Company Methods of manufacturing dipped bladder molding mandrels for manufacturing tubular shafts
US6719555B2 (en) 1999-10-07 2004-04-13 Fibrex Insulations, Inc. Apparatus for making pipe insulation
US6364649B1 (en) 1999-10-07 2002-04-02 Fibrex Insulations, Inc. Apparatus for making pipe insulation
US20020039605A1 (en) * 1999-10-07 2002-04-04 Moore Geoffrey H. Method for making pipe insulation
US20020048616A1 (en) * 1999-10-07 2002-04-25 Moore Geoffrey H. Apparatus for making pipe insulation
US6586110B1 (en) 2000-07-07 2003-07-01 Delphi Technologies, Inc. Contoured metal structural members and methods for making the same
US6949282B2 (en) 2000-07-07 2005-09-27 Delphi Technologies, Inc. Contoured crushable composite structural members and methods for making the same
US6893733B2 (en) 2000-07-07 2005-05-17 Delphi Technologies, Inc. Modified contoured crushable structural members and methods for making the same
US20050089707A1 (en) * 2000-07-07 2005-04-28 Delphi Technologies, Inc. Shaped contoured crushable structural members and methods for making the same
US6821638B2 (en) 2000-07-07 2004-11-23 Delphi Technologies, Inc. Shaped contoured crushable structural members and methods for making the same
EP1342556A1 (en) * 2002-03-09 2003-09-10 Airbus Deutschland GmbH Process for producing a fiber reinforced composite component
US20060273491A1 (en) * 2002-08-09 2006-12-07 The Boeing Company Preforming Thermoplastic Ducts
US7846287B2 (en) 2002-08-09 2010-12-07 The Boeing Company Preforming thermoplastic ducts
US20040028365A1 (en) * 2002-08-09 2004-02-12 Abds-Sami Malik Metal oxide coated fiber and methods for coating an optical fiber with a metal oxide coating
US20040026819A1 (en) * 2002-08-09 2004-02-12 The Boeing Company Post-forming of thermoplastic ducts
US20040026825A1 (en) * 2002-08-09 2004-02-12 The Boeing Company Preforming thermoplastic ducts
US7014450B2 (en) 2002-08-09 2006-03-21 The Boeing Company Thermoplastic sheet forming apparatus and method
US20060103050A1 (en) * 2002-08-09 2006-05-18 The Boeing Company Thermoplastic sheet forming apparatus and method
US7097804B2 (en) 2002-08-09 2006-08-29 The Boeing Company Thermoplastic laminate duct
US7112054B2 (en) 2002-08-09 2006-09-26 The Boeing Company Consolidation joining of thermoplastic laminate ducts
US7128558B2 (en) 2002-08-09 2006-10-31 The Boeing Company Post-forming of thermoplastic ducts
US20040026015A1 (en) * 2002-08-09 2004-02-12 The Boeing Company Consolidation joining of thermoplastic laminate ducts
US7153124B2 (en) 2002-08-09 2006-12-26 The Boeing Company Preforming thermoplastic ducts
US20070013105A1 (en) * 2002-08-09 2007-01-18 The Boeing Company Post-Forming of Thermoplastic Ducts
US20040026826A1 (en) * 2002-08-09 2004-02-12 The Boeing Company Thermoplastic sheet forming apparatus and method
US20070107832A1 (en) * 2002-08-09 2007-05-17 The Boeing Company Consolidation Joining of Thermoplastic Laminate Ducts
US7608213B2 (en) 2002-08-09 2009-10-27 The Boeing Company Thermoplastic sheet forming apparatus and method
US7553388B2 (en) 2002-08-09 2009-06-30 The Boeing Company Consolidation joining of thermoplastic laminate ducts
US7182293B2 (en) 2004-04-27 2007-02-27 The Boeing Company Airfoil box and associated method
US8438857B2 (en) 2006-07-19 2013-05-14 Rohr, Inc. Aircraft engine inlet having zone of deformation
US20080016844A1 (en) * 2006-07-19 2008-01-24 Shutrump Jeffrey D Aircraft engine inlet having zone of deformation
US7721525B2 (en) 2006-07-19 2010-05-25 Rohr, Inc. Aircraft engine inlet having zone of deformation
US20110167606A1 (en) * 2006-07-19 2011-07-14 Rohr, Inc. Aircraft engine inlet having zone of deformation
EP2045069A1 (en) * 2007-10-04 2009-04-08 The Goodyear Tire & Rubber Company Tire bead separation method and device
US20090089992A1 (en) * 2007-10-04 2009-04-09 Richard David Vargo Tire bead separation method and device
US7963018B2 (en) * 2007-10-04 2011-06-21 The Goodyear Tire & Rubber Company Tire bead separation method and device
US20090308477A1 (en) * 2008-06-13 2009-12-17 Geislinger Gmbh Method for manufacturing a hollow shaft with at least one integral flange made of fiber composite
US8813335B2 (en) * 2008-06-13 2014-08-26 Ellergon Antriebstechnik Gesellschaft M.B.H. Method for manufacturing a hollow shaft with at least one integral flange made of fiber composite
US10006568B2 (en) 2016-06-06 2018-06-26 United Technologies Corporation Double walled tube and manufacture thereof
CN106493965A (en) * 2016-10-21 2017-03-15 北京化工大学 A kind of continuously elongated device and method for strengthening composite plastic pipe
EP3342584A1 (en) * 2016-12-30 2018-07-04 Airbus Operations GmbH Membrane tool for reshaping reinforcing fibre layers for pre-shaped t-shaped profiles
US11273610B2 (en) * 2019-03-21 2022-03-15 Goodrich Corporation Manufacturing methods for composite driveshafts
US11260605B2 (en) 2020-01-21 2022-03-01 Goodrich Corporation Flexible thermoplastic composite coupling and method of manufacture

Similar Documents

Publication Publication Date Title
US5225016A (en) Method of manufacturing an advanced composite duct having integral ribs
EP0579163B1 (en) Structural element formed of a fiber reinforced thermoplastic material and method of manufacture
US6071460A (en) Method of manufacturing a golf shaft of complex shape by internal bladder pressurization
US5071506A (en) Equipment for making composite tubes including an inflatable heated bladder and a composite mold having a negative coefficient of thermal expansion
US6361840B2 (en) Injection molded, rigidized bladder with varying wall thickness for manufacturing composite shafts
EP2038100B1 (en) Method and moulding core for producing a fibre composite component for aviation and spaceflight
US4859380A (en) Method and apparatus for producing fiber-reinforced rubber hose
US3265795A (en) Method of skin molding
JPH07241915A (en) Manufacture of frame for game racket
EP0311400B1 (en) Process and equipment for making composite tubes
US20230173771A1 (en) Method for manufacturing tube body made of fiber-reinforced resin
CN1069577C (en) Method and apparatus of manufacturing synchronous drive belt with teeth which are axially interlocked with mold surface
GB2250466A (en) Moulding a hollow golf club shaft from composite fibre/resin material
US4614631A (en) Process for screw-cutting in a tube or link made from a composite carbon fiber based material coated with polymerized resin
US3377657A (en) Apparatus for molding a reinforced hollow plastic article
JP4227299B2 (en) Manufacturing method of flanged tubular product made of fiber reinforced plastic
JP2524315B2 (en) FRP coil spring manufacturing method
US2945531A (en) Apparatus for making a reinforced fiber glass tube
JP3792359B2 (en) Manufacturing apparatus for hollow fiber reinforced resin molded body and manufacturing method thereof
JPH05177722A (en) Structure of composite fiber reinforced resin tube and its manufacture
WO1996007533A1 (en) Method of making composite product of tubular structure using clamshell mold
US20220281183A1 (en) Expansion held prepeg composite
JP2024028003A (en) Manufacturing method of tubular body
JP3675786B2 (en) Continuous production equipment for FRP square pipes
JPS6143537A (en) Manufacture of cylindrical material made of fiber-reinforced plastics having heat insulation layer

Legal Events

Date Code Title Description
AS Assignment

Owner name: ROHR INDUSTRIES, INC., CALIFORNIA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:SARH, BRANKO;REEL/FRAME:005802/0209

Effective date: 19910726

AS Assignment

Owner name: ROHR, INC. A CORP. OF DE

Free format text: CHANGE OF NAME;ASSIGNOR:ROHR INDUSTRIES, INC., A CORP. OF DE;REEL/FRAME:006142/0573

Effective date: 19911210

REMI Maintenance fee reminder mailed
LAPS Lapse for failure to pay maintenance fees
FP Lapsed due to failure to pay maintenance fee

Effective date: 19970709

STCH Information on status: patent discontinuation

Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362